Gas Turbine Airfoil Cooling Passage Rib Segmentation
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Solution Overview
Problem
The structural weakening of gas turbine engine blades due to internal cooling passages and the need to enhance airflow to airfoil cavities without compromising structural integrity, as existing solutions like ribs and layered cores can reduce airflow and increase stress.
Innovation Solution
A cooling passage configuration that includes a leading edge passageway, a trailing edge passageway, and multiple intermediate passageways arranged chord-wise, with ribs extending between pressure and suction side walls to separate passageways and a riblet in the root that connects to the airfoil body, allowing increased airflow while maintaining structural integrity.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If ribs are used in cooling passages to strengthen the blade, then structural integrity is improved, but airflow to airfoil cavities is reduced
Solution Approach 1:
The rib structure is segmented into two distinct parts: a first rib portion within the root region and a second rib portion within the airfoil body. This segmentation allows the first portion to provide structural support where stress is highest, while the second portion maintains cooling passage openness to allow adequate airflow to the airfoil cavities, thus resolving the contradiction between structural integrity and airflow quantity.
2Strength
If multiple layered cores are used with ribs, then structural strength is improved, but the amount of air available to airfoil cavities is greatly reduced
Solution Approach 1:
The rib structure exhibits local quality by having different configurations in different regions: in the root region where structural strength is critical, the first rib portion is present to provide support, while in the airfoil body region where airflow is critical, the second rib portion is designed to be less intrusive or absent in specific areas, allowing adequate air supply to the cavities. This localized differentiation resolves the contradiction between structural strength and air availability.
3Strength
If ribs extend the entire span from root to tip, then structural integrity is improved, but cooling airflow distribution is compromised
Solution Approach 1:
The rib is divided into a first rib portion in the root and a second rib portion in the airfoil body, allowing each segment to serve its specific function. The first portion provides structural support at the root, while the second portion is configured to minimize interference with cooling airflow distribution to the airfoil cavities, thus resolving the contradiction between structural integrity and cooling airflow distribution.
Data Source
Figure 1
Figure 2A~2B
Figure 3A~4B
AI summary
An airfoil (78) for a gas turbine engine (20) includes an airfoil body that extends in a radial direction (R) from a support (74). The airfoil body has pressure and suction side walls (86,88) joined at leading and trailing edges (82,84) to provide an exterior airfoil surface. A chord-wise direction (C) extends between the leading and trailing edges (82,84) and a thickness direction (T) transverse to chord-wise direction (C) and extending between the pressure and suction side walls (86,88). Cooling passages (92) extend from the support (74) into the airfoil body. The cooling passages (92) include adjacent passageways (94,96,98,100) in the thickness direction and are separated by a chord-wise wall. One of the adjacent passageways (94,96,98,100) is adjacent to another passageway (94,96,98,100) in the chord-wise direction (C) and is separated by a rib (112a,112b,112c) in the thickness direction (T). The rib (112a,112b,112c) is discontinued at a location along the radial direction (R) to provide an opening (115;215) that fluidly connects one of the adjacent passageways (94,96,98,100) to the other passageway (94,96,98,100).